Abstract
A combination of time-resolved particle-image velocimetry (TR-PIV) with unsteady pressure measurement is used to analyze the unsteady flow over an aeroelastic supercritical BAC 3-11 transport-type wing configuration in sub-transonic flow. The dynamic interaction between shock wave and, turbulent separation is the essential feature of the unsteady flow causing a distinct self-induced oscillation of both the wing structure and the flow field. Results from wind tunnel experiments with a variation of the free stream Mach number at Reynolds numbers O 7 m -1 ) are analyzed regarding the origin and nature of the unsteady shock – boundary – layer interaction. TR-PIV results are presented for a flow case with weak shock and incipient separation as well as for a case with medium shock strength and full scale trailing edge separation. The visualization of the flow field, which is time-resolved regarding the shock wave oscillation, demonstrates the two-fold nature of the shockboundary layer interaction, on the one hand being the origin of aerodynamic unsteadiness in case of marginally separated flow, on the other hand damping the fluctuation level in case of a full-scale separation.
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